CN115950316A - Automatic initiating explosive device protection and protection circuit for carrier rocket - Google Patents
Automatic initiating explosive device protection and protection circuit for carrier rocket Download PDFInfo
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- CN115950316A CN115950316A CN202211215788.9A CN202211215788A CN115950316A CN 115950316 A CN115950316 A CN 115950316A CN 202211215788 A CN202211215788 A CN 202211215788A CN 115950316 A CN115950316 A CN 115950316A
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Abstract
The invention relates to an automatic protection and protection circuit for an initiating explosive device for a carrier rocket, belonging to the technical field of protecting the initiating explosive device of the carrier rocket; comprises electromagnetic relays J1-J4, magnetic latching relays K1-Kn,
A current limiting resistor,
An initiating explosive device and an initiating explosive device bus; each electromagnetic relay is provided with 6 contacts from 1 to 6; each magnetic latching relay is provided with a contact 1 and a contact 2; each magnetic latching relay is provided with a front exciting coil and a rear exciting coil; the automatic protection, the solution protection and other operations of the initiating explosive device before the launch of the carrier rocket are realized; the invention realizes automatic protection and release control before the firing of the initiating explosive device, reduces the operation of the personnel for going up the arrow,the operation risk is reduced, and the safety of initiating explosive devices is improved.
Description
Technical Field
The invention belongs to the technical field of protection of initiating explosive devices of carrier rockets, and relates to an automatic protecting and protecting circuit of initiating explosive devices for carrier rockets.
Background
At present, after initiating explosive devices are connected to a control circuit, in order to prevent the initiating explosive devices from being exploded mistakenly, short-circuit protection plugs are usually adopted to short circuit the positive end and the negative end of each initiating explosive device, the initiating explosive device short-circuit protection plugs are manually taken down before being launched, the work belongs to rocket loading operation before launching, and the risk is high.
Disclosure of Invention
The technical problem solved by the invention is as follows: the automatic protection and protection circuit for the initiating explosive device for the carrier rocket overcomes the defects of the prior art, realizes automatic protection and protection control before the initiating explosive device is shot, reduces the operation of people for shooting, reduces the operation risk, and improves the safety of the initiating explosive device.
A large number of initiating explosive devices are used on the carrier rocket to complete key actions such as ignition, separation and the like of the rocket. In order to ensure the safety of initiating explosive devices before rocket launching, short circuit heads are generally adopted to short-circuit the positive end and the negative end of the initiating explosive devices, and the short circuit heads are taken down by a person who goes up an arrow before the rocket is launched. Along with the further improvement of the rocket launching safety requirement, unattended operation is required to be realized before the rocket is launched, and the mode of manually plugging and unplugging the short-circuit protection head cannot be applied.
The technical scheme of the invention is as follows:
an automatic protection and protection circuit for initiating explosive devices for carrier rockets comprises electromagnetic relays J1-J4, magnetic latching relays K1-Kn,
A current-limiting resistor>
Each initiating explosive device and each initiating explosive device bus; each electromagnetic relay is provided with 6 contacts from 1 to 6; each magnetic latching relay is provided with a contact 1 and a contact 2; each magnetic latching relay is provided with a front exciting coil and a rear exciting coil;
the electromagnetic relays J1-J4 are connected in parallel and then are connected with an external ground measurement and control system;
the contacts 1 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a first circuit; the contacts 2 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a second circuit; front exciting coils of the magnetic latching relays K1-Kn are connected in parallel to form a third circuit; the second circuit is connected with the third circuit in parallel, is connected with the first circuit in series and then is connected with an external ground test launch and control system;
the contacts 5 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a fourth circuit; the contacts 6 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a fifth circuit; rear exciting coils of the magnetic latching relays K1-Kn are connected in parallel to form a sixth circuit; the fifth circuit is connected with the sixth circuit in parallel, is connected with the fourth circuit in series and then is connected with an external ground surface measurement and control system;
the contacts 3 of the electromagnetic relays J1-J4 are connected in parallel and then in series and then are connected with an external carrier rocket measuring system;
contacts 4 of the electromagnetic relays J1-J4 are respectively connected with an external carrier rocket measuring system;
in the magnetic latching relays K1-Kn, every 2 contacts 2 of the magnetic latching relays are divided into a group, and the contacts 2 of the magnetic latching relays K1-Kn are divided into
Group (d); each current-limiting resistor and 1 initiating explosive device are connected in series to form 1 group of series circuit; the solution and protection point positions of the 2 magnetic latching relay contacts 2 in each group are respectively connected with an external carrier rocket measuring system, and the protection point positions of the 2 magnetic latching relay contacts 2 are connected with the initiating explosive device bus after being connected with the series circuit in parallel.
In the above automatic protection and protection circuit for initiating explosive device for carrier rocket, n is even number and n is greater than 2.
In the automatic initiating explosive device protection and solution circuit for the carrier rocket, when an external ground test and launch control system sends an initiating explosive device solution control instruction to the automatic protection and solution circuit, all contacts of the electromagnetic relays J1-J4 act simultaneously; the contact 1, the contact 4 and the contact 5 of the electromagnetic relays J1-J4 are changed into a closed state from an open state, and meanwhile, the contact 2, the contact 3 and the contact 6 of the electromagnetic relays J1-J4 are changed into an open state from a normally closed state; and finishing the control of the initiating explosive device.
In the automatic protection and protection circuit for the initiating explosive device for the carrier rocket, the states and the control-releasing states of the contact 3 and the contact 4 of the electromagnetic relays J1-J4 are respectively sent to an external ground measurement and control system and an external carrier rocket measurement system.
In the automatic initiating explosive device protection and solution circuit for the carrier rocket, when an external ground measurement and launch control system sends out an initiating explosive device protection instruction to the automatic protection and solution circuit, a front exciting coil of a magnetic latching relay K1-Kn is driven, and a contact 1 of the magnetic latching relay K1-Kn is changed into a closed state from an open state; and the contact 2 of the magnetic latching relays K1-Kn is switched from the disconnection point to the protection point to complete the short-circuit protection of the initiating explosive device.
In the automatic protection and protection circuit for the initiating explosive device for the carrier rocket, the state of the contact 1 of the magnetic latching relay K1-Kn, the point position state of the contact 2 and the short-circuit protection state of the initiating explosive device are respectively transmitted to an external ground test, launch and control system and an external carrier rocket measurement system.
In the automatic initiating explosive device protection and solution circuit for the carrier rocket, when an external ground measurement and control system sends an initiating explosive device solution instruction to the automatic protection and solution circuit, a rear exciting coil of a magnetic latching relay K1-Kn is driven; the contact 1 of the magnetic latching relay K1-Kn is changed into a closed state from an open state; and the contact 2 of the magnetic latching relays K1-Kn is switched from the protection point position communication to the Jie Bao point position communication, so that the solution and the protection of the initiating explosive device circuit are completed.
In the automatic initiating explosive device protection and solution circuit for the carrier rocket, the state of the contact 1 of the magnetic latching relay K1-Kn, the point position state of the contact 2 and the solution state of an initiating explosive device line are respectively transmitted to an external ground test, transmission and control system and an external carrier rocket measurement system.
In the automatic initiating explosive device protection and protection circuit for the carrier rocket, the initiating explosive device control command, the initiating explosive device protection command and the initiating explosive device protection command are all 28V charged pulse commands, and the pulse width is 100ms.
In the automatic protection and protection circuit for the initiating explosive device for the carrier rocket, the automatic protection and protection circuit sends the state of the protection and control, the short-circuit protection state of the initiating explosive device, the state of the protection and protection of the initiating explosive device line, the state of the contact 1 of the magnetic latching relays K1-Kn and the point position state of the contact 2 to an external ground test, launch and control system and an external carrier rocket measurement system through the RS422 bus.
Compared with the prior art, the invention has the beneficial effects that:
(1) According to the invention, the initiating explosive device control instruction positive terminal and the initiating explosive device power supply negative bus are introduced into the initiating explosive device automatic protection and protection device, and the relay contact inside the initiating explosive device automatic protection and protection device is utilized to carry out short circuit or disconnection, so that the short circuit protection or protection function of the initiating explosive device is realized;
(2) In order to avoid abnormal state turnover caused by abnormal instructions or interference drive of magnetic latching relays K1-Kn, four groups of electromagnetic relays J1-J4 contacts are connected in parallel and then connected in series to form a normally closed contact pair, coils of the magnetic latching relays K1-Kn are subjected to short circuit locking, if the magnetic latching relays K1-Kn need to be controlled, a ground device of a carrier rocket needs to send a control releasing instruction to power the coils of the relays J1-J4, the contacts of the relays J1-J4 are controlled to be opened, and the coils of the magnetic latching relays K1-Kn are unlocked;
(3) The invention connects the normally open contacts of the relays J1-J4 which are connected in series after being connected in parallel on the path of the initiating explosive device protection instruction and the initiating explosive device protection instruction sent by the rocket ground equipment, and the initiating explosive device protection/protection instruction and the control instruction form a relay interlocking circuit, thereby improving the initiating explosive device protection/protection instruction control safety;
drawings
FIG. 1 is a diagram of an automatic protection and protection circuit according to the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides an automatic protection and solution circuit for initiating explosive devices for a carrier rocket, which realizes automatic protection, solution and other operations of the initiating explosive devices before launching of the carrier rocket, realizes automatic protection and solution control before launching of the initiating explosive devices, reduces the operation of people for getting on the rocket, reduces the operation risk and improves the safety of the initiating explosive devices.
An automatic protection and protection circuit for initiating explosive device, as shown in figure 1, comprises electromagnetic relays J1-J4, magnetic latching relays K1-Kn,
A current-limiting resistor>
An initiating explosive device and an initiating explosive device bus; each electromagnetic relay is provided with 6 contacts from 1 to 6; each magnetic latching relay is provided with a contact 1 and a contact 2; and each magnetic keeper relayThe electric appliance is provided with a front exciting coil and a rear exciting coil; n is an even number and n is greater than 2.
The invention designs the contact of each electromagnetic relay and each magnetic latching relay in detail, which comprises the following steps:
the electromagnetic relays J1-J4 are connected in parallel and then connected with an external ground measurement and control system.
The contacts 1 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a first circuit; the contacts 2 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a second circuit; front exciting coils of the magnetic latching relays K1-Kn are connected in parallel to form a third circuit; the second circuit and the third circuit are connected in parallel and are connected with the first circuit in series and then are connected with an external ground measurement and launch control system.
The contacts 5 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a fourth circuit; the contacts 6 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a fifth circuit; rear exciting coils of the magnetic latching relays K1-Kn are connected in parallel to form a sixth circuit; the fifth circuit and the sixth circuit are connected in parallel and are connected with the fourth circuit in series and then are connected with an external ground measurement and launch control system.
The contacts 3 of the electromagnetic relays J1-J4 are connected in parallel and then in series and then are connected with an external carrier rocket measuring system.
Contacts 4 of the electromagnetic relays J1-J4 are respectively connected with an external carrier rocket measuring system.
The contacts 1 of the magnetic latching relays K1-Kn are respectively connected with an external carrier rocket measuring system.
In the magnetic latching relays K1-Kn, every 2 contacts 2 of the magnetic latching relays are divided into a group, and the contacts 2 of the magnetic latching relays K1-Kn are divided into
Group (iv); each current-limiting resistor is connected with 1 initiating explosive device in series to form 1 group of series circuits; the solution and protection point positions of the 2 magnetic latching relay contacts 2 in each group are respectively connected with an external carrier rocket measuring system, and the protection point positions of the 2 magnetic latching relay contacts 2 are connected with the initiating explosive device bus after being connected with the series circuit in parallel.
In actual work, the external ground measurement and control system transmits instructions through the three instructions and the automatic protection and protection circuit, and the three instructions are an initiating explosive device control instruction, an initiating explosive device protection instruction and an initiating explosive device protection instruction. The specific circuit working process is as follows:
when the external ground measurement and control system sends out an initiating explosive device control releasing instruction to the automatic protection and protection releasing circuit, all contacts of the electromagnetic relays J1-J4 act simultaneously; the contact 1, the contact 4 and the contact 5 of the electromagnetic relays J1-J4 are changed into a closed state from an open state, and the contact 2, the contact 3 and the contact 6 of the electromagnetic relays J1-J4 are changed into an open state from a normally closed state; and finishing the control of the initiating explosive device. Meanwhile, the states and the control releasing states of the contact 3 and the contact 4 of the electromagnetic relays J1-J4 are respectively sent to an external ground measuring, transmitting and controlling system and an external carrier rocket measuring system.
When an external ground measurement and control system sends an initiating explosive device protection instruction to the automatic protection and protection circuit, a front exciting coil of the magnetic latching relay K1-Kn is driven, and a contact 1 of the magnetic latching relay K1-Kn is changed into a closed state from an open state; and the contact 2 of the magnetic latching relays K1-Kn is switched from the disconnection point to the protection point to complete the short-circuit protection of the initiating explosive device. The state of a contact 1 of the magnetic latching relay K1-Kn, the point position state of a contact 2 and the short-circuit protection state of the initiating explosive device are respectively transmitted to an external ground test, launch and control system and an external carrier rocket measurement system.
When an external ground measurement and launch control system sends an initiating explosive device protecting command to the automatic protection and protecting circuit, a rear exciting coil of the magnetic latching relay K1-Kn is driven; the contact 1 of the magnetic latching relay K1-Kn is changed from an open state to a closed state; and the contact 2 of the magnetic latching relays K1-Kn is switched from the protection point position communication to the Jie Bao point position communication, so that the solution and the protection of the initiating explosive device circuit are completed. The state of a contact 1 of the magnetic latching relay K1-Kn, the point position state of a contact 2 and the state of the solution of the initiating explosive device line are respectively transmitted to an external ground testing, transmitting and controlling system and an external carrier rocket measuring system.
The initiating explosive device control command, the initiating explosive device protection command and the initiating explosive device protection command are all 28V charged pulse commands, and the pulse width is 100ms.
The automatic protection and protection circuit sends the protection state, the short-circuit protection state of the initiating explosive device, the protection state of the initiating explosive device line, the state of the contact 1 of the magnetic latching relays K1-Kn and the point position state of the contact 2 to an external ground test, launch and control system and an external carrier rocket measurement system through an RS422 bus.
The initiating explosive device control instruction positive end and the initiating explosive device power supply negative bus are led into the initiating explosive device automatic protection and protection device, and a relay contact inside the initiating explosive device automatic protection and protection device is utilized to carry out short circuit or disconnection, so that the short circuit protection or protection function of the initiating explosive device is realized. The initiating explosive device automatic protection and protection device receives a control instruction from rocket ground equipment to complete automatic protection and protection of the initiating explosive device.
Further, in order to avoid abnormal state turnover caused by abnormal instructions or interference drive of the magnetic latching relays K1-Kn, the magnetic latching relays K1-Kn coils of a normally closed contact pair formed by connecting four groups of relays J1-J4 in parallel and then in series are used for short circuit locking, if the magnetic latching relays K1-Kn need to be controlled, a ground device of a carrier rocket needs to send out a control releasing instruction to power up the relays J1-J4 coils, the relays J1-J4 are controlled to be opened, and locking of the magnetic latching relays K1-Kn is released.
Furthermore, a normally open contact of the relays J1-J4 which are connected in parallel and then connected in series is connected in series on a path of the rocket ground equipment for sending the initiating explosive device protection instruction and the initiating explosive device protection instruction, and the initiating explosive device protection/protection instruction and the control-release instruction form a relay interlocking circuit, so that the control safety of the initiating explosive device protection/protection instruction is improved.
Further, the on-off state of the contacts of the relays J1-J4, the on-off state of the contacts of the magnetic latching relays K1-Kn, the total on-off state of the contacts of the relays J1-J4 after being connected in parallel and then in series, and the total on-off state of the contacts of the magnetic latching relays K1-Kn after being connected in series are collected by the automatic initiating explosive device protecting and protecting device and are sent to the rocket measuring system and the rocket ground equipment through the RS422 bus.
Further, after the initiating explosive device protection device finishes initiating explosive device protection before shooting, the relays K1-Kn are in disconnection, the initiating explosive device automatic protection and protection device samples the contact reverse state used for initiating explosive device protection after the relays K1-Kn are connected in series, the sampling circuit is physically isolated from the initiating explosive device control circuit, and the fact that the internal sampling circuit in the initiating explosive device protection and protection state does not influence the initiating explosive device control circuit is guaranteed.
Furthermore, in order to reduce the influence of external vibration and impact on magnetic latching relays K1-Kn armatures, when the magnetic latching relays K1-Kn are arranged in a layout mode, two magnetic latching relays connected in series are vertically arranged, and the sensitive directions of the two relays are prevented from being in one direction.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make possible variations and modifications of the present invention using the method and the technical contents disclosed above without departing from the spirit and scope of the present invention, and therefore, any simple modifications, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention are all within the scope of the present invention.
Claims (10)
1. An initiating explosive device automatic protection and solution protection circuit for a carrier rocket is characterized in that: comprises electromagnetic relays J1-J4, magnetic latching relays K1-Kn,
A current-limiting resistor>
Each initiating explosive device and each initiating explosive device bus; each electromagnetic relay is provided with 6 contacts from 1 to 6; each magnetic latching relay is provided with a contact 1 and a contact 2; each magnetic latching relay is provided with a front exciting coil and a rear exciting coil;
the electromagnetic relays J1-J4 are connected in parallel and then connected with an external ground measurement and control system;
the contacts 1 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a first circuit; the contacts 2 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a second circuit; front exciting coils of the magnetic latching relays K1-Kn are connected in parallel to form a third circuit; the second circuit is connected with the third circuit in parallel, is connected with the first circuit in series and then is connected with an external ground test launch and control system;
the contacts 5 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a fourth circuit; the contacts 6 of the electromagnetic relays J1-J4 are connected in parallel and then connected in series to form a fifth circuit; rear exciting coils of the magnetic latching relays K1-Kn are connected in parallel to form a sixth circuit; the fifth circuit is connected with the sixth circuit in parallel, is connected with the fourth circuit in series and then is connected with an external ground surface measurement and control system;
the contacts 3 of the electromagnetic relays J1-J4 are connected in parallel, then connected in series and then connected with an external carrier rocket measuring system;
contacts 4 of the electromagnetic relays J1-J4 are respectively connected with an external carrier rocket measuring system;
the contacts 1 of the magnetic latching relays K1-Kn are respectively connected with an external carrier rocket measuring system;
in the magnetic latching relays K1-Kn, every 2 contacts 2 of the magnetic latching relays are divided into a group, and the contacts 2 of the magnetic latching relays K1-Kn are divided into
Group (d); each current-limiting resistor is connected with 1 initiating explosive device in series to form 1 group of series circuits; the solution and protection point positions of the 2 magnetic latching relay contacts 2 in each group are respectively connected with an external carrier rocket measuring system, and the protection point positions of the 2 magnetic latching relay contacts 2 are connected with the initiating explosive device bus after being connected with the series circuit in parallel.
2. The automatic protection and protection circuit for initiating explosive device for carrier rocket according to claim 1, characterized in that: n is an even number and n is greater than 2.
3. The automatic protection and protection circuit for initiating explosive device for carrier rocket according to claim 1, characterized in that: when the external ground surface measurement and control system sends an initiating explosive device control releasing instruction to the automatic protection and protection circuit, all contacts of the electromagnetic relays J1-J4 act simultaneously; the contact 1, the contact 4 and the contact 5 of the electromagnetic relays J1-J4 are changed into a closed state from an open state, and the contact 2, the contact 3 and the contact 6 of the electromagnetic relays J1-J4 are changed into an open state from a normally closed state; and finishing the control of the initiating explosive device.
4. The automatic protection and protection circuit for initiating explosive device for carrier rocket according to claim 3, characterized in that: the states and the control releasing states of the contacts 3 and 4 of the electromagnetic relays J1-J4 are respectively sent to an external ground measuring, launching and controlling system and an external carrier rocket measuring system.
5. The automatic protection and protection circuit for initiating explosive device for carrier rocket according to claim 4, characterized in that: when an external ground measurement and control system sends an initiating explosive device protection instruction to the automatic protection and protection circuit, a front exciting coil of the magnetic latching relay K1-Kn is driven, and a contact 1 of the magnetic latching relay K1-Kn is changed into a closed state from an open state; and the contact 2 of the magnetic latching relays K1-Kn is switched from the disconnection point to the protection point to complete the short-circuit protection of the initiating explosive device.
6. The automatic protection and protection circuit for initiating explosive device for carrier rocket according to claim 5, characterized in that: the state of a contact 1 of the magnetic latching relay K1-Kn, the point position state of a contact 2 and the short-circuit protection state of the initiating explosive device are respectively transmitted to an external ground test, launch and control system and an external carrier rocket measurement system.
7. The automatic protection and protection circuit for initiating explosive device for carrier rocket according to claim 6, characterized in that: when an external ground measurement and launch control system sends an initiating explosive device protecting command to the automatic protection and protecting circuit, a rear exciting coil of the magnetic latching relay K1-Kn is driven; the contact 1 of the magnetic latching relay K1-Kn is changed from an open state to a closed state; and the contact 2 of the magnetic latching relays K1-Kn is switched from the protection point position communication to the Jie Bao point position communication, so that the solution and the protection of the initiating explosive device circuit are completed.
8. The automatic protection and protection circuit for initiating explosive device for carrier rocket according to claim 7, characterized in that: the state of a contact 1 of the magnetic latching relay K1-Kn, the point position state of the contact 2 and the state of the solution of the initiating explosive device line are respectively transmitted to an external ground testing, transmitting and controlling system and an external carrier rocket measuring system.
9. The automatic protection and release circuit of initiating explosive device for carrier rocket according to claim 8, characterized in that: the initiating explosive device control command, the initiating explosive device protection command and the initiating explosive device protection command are all 28V charged pulse commands, and the pulse width is 100ms.
10. The automatic protection and protection circuit for initiating explosive device for carrier rocket according to claim 9, characterized in that: the automatic protection and protection circuit sends the protection state, the short-circuit protection state of the initiating explosive device, the protection state of the initiating explosive device line, the state of the contact 1 of the magnetic latching relay K1-Kn and the point position state of the contact 2 to an external ground test, launch and control system and an external carrier rocket measurement system through an RS422 bus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211215788.9A CN115950316A (en) | 2022-09-30 | 2022-09-30 | Automatic initiating explosive device protection and protection circuit for carrier rocket |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211215788.9A CN115950316A (en) | 2022-09-30 | 2022-09-30 | Automatic initiating explosive device protection and protection circuit for carrier rocket |
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| Publication Number | Publication Date |
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| CN115950316A true CN115950316A (en) | 2023-04-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211215788.9A Pending CN115950316A (en) | 2022-09-30 | 2022-09-30 | Automatic initiating explosive device protection and protection circuit for carrier rocket |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116379846A (en) * | 2023-06-06 | 2023-07-04 | 北京星河动力装备科技有限公司 | Rocket flight time sequence verification device and system |
-
2022
- 2022-09-30 CN CN202211215788.9A patent/CN115950316A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116379846A (en) * | 2023-06-06 | 2023-07-04 | 北京星河动力装备科技有限公司 | Rocket flight time sequence verification device and system |
| CN116379846B (en) * | 2023-06-06 | 2023-09-05 | 北京星河动力装备科技有限公司 | Rocket flight time sequence verification device and system |
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